nasa asteroid redirect mission - dmns galaxy guide portal · asteroid targets with detailed mission...
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General Information
Reference Information
Redirect & Explore Select
Image Develop Capabilities
NASA Asteroid
Redirect Mission Identify
General Information - Asteroid Strategy and Mission Concept
Map of Cis-Lunar Space
38,200 miles 38,200 miles
248,500 miles
22,400 miles
DRO
Credit: NASA
Strategy In April 2010, President Barack Obama announced a human mission to an asteroid. The
budget leverages NASA’s human and robotic activities for the mission and also accelerates
efforts to address potentially hazardous asteroids:
To protect our planet.
To advance exploration capabilities and technologies for human space flight.
To learn how to best utilize space resources.
- The FY14 budget aligns relevant portions of NASA’s science, space technology, and human
exploration capabilities to plan for the mission.
Concept Capture and redirect a 16.4-32.8 ft (with
45.9 ft maximum dimension) up to
2.2 million lbs (1000 metric ton) near Earth
asteroid in a DRO in trans-lunar space.
Enable astronaut missions to the
asteroid as early as 2021.
Map Legend LEO - Low Earth orbit
MEO - Medium Earth orbit
HEO - High Earth orbit
GEO - Geosynchronous Earth orbit
LLO - Lunar low orbit
DRO - Distant Retrograde Orbit
L1 & L2 - Lagrange point 1 & 2
Asteroid Mission Overview
Legend:
LGA - Lunar Gravity Assist
SLS - Space Launch System S/A - Solar Array
SEP - Solar Electric Propulsion
DRO - Distant Retrograde Orbit
Credit: NASA
2) Separation & S/A Deployment
2) Separation & S/A Deployment
Credit: NASA
Asteroid Mission Preliminary Schedule Credit: NASA
Legend:
SST - Space Surveillance Telescope
PS-2 - Panoramic Survey Telescope
and Response System
SLS - Space Launch System
GEO - Geostationary Earth Orbit
EM-1 & EM-2 - Exploration Mission 1 and 2
Capabilities Required for First Steps to Destinations
The capabilities required for the first steps to Mars and other destinations as well as
the International Space Station (ISS) and Asteroid Redirect Mission are shown.
Credit: NASA
2013 Mission Formulation Review (MFR)
The MFR results were based on or enabled by:
The Asteroid Redirect Mission Feasibility Study, April 2, 2013, which was in turn
based on previous studies (e.g., Keck Institute for Space Studies, April 2, 2012, KISS);
NASA investments in asteroid observation, low thrust mission tools/design, solar
electric propulsion technology and experience from various Science Mission
Directorate and Human Exploration and Operations Mission Directorate missions.
The MFR reviewed the results of the three reference mission concept studies:
1) Identifying candidate asteroid targets for the reference mission;
2) Conducting a feasibility assessment of robotic redirection of a small near Earth
asteroid (NEA);
3) Conducting an assessment of the astronaut exploration and sampling of the asteroid
using the Orion.
The MFR also reviewed three high-level trade studies to examine alternatives (e.g.
shorter studies than the reference mission):
1) Alternative approach to the robotic mission;
2) Demonstrate planetary defense and retrieve boulder(s) from a large NEA (potentially
hazardous size);
3) Alternative Robotic Mission System trade studies included:
-- Capture System;
-- Solar Electric Propulsion (SEP).
The MFR determined the Asteroid Redirect Mission is technically and
programmatically feasible within the constrained budget environment during the
mission years.
Identify - NASA Selects an Asteroid
Credit: NASA NASA must first identify a suitable
asteroid target. The ideal space rock is
one that is small, 16.4-32.8 ft with a
45.9 ft maximum dimension, and close
to Earth. The size of the asteroid is
important. If something were to go
wrong, this asteroid would be small
enough to burn up before it enters
Earth's atmosphere.
Ground and space based Near Earth
Asteroid target detection,
characterization and selection will be
used. The majority of asteroids fall into three categories:
C-type (carbonaceous) includes more than 75 percent of known asteroids. Very dark with an
albedo of 0.03-0.09. Composition is thought to be similar to the Sun, depleted in hydrogen,
helium, and other volatiles. C-types inhabit the main asteroid belt's outer regions. The main
asteroid belt is the region of the Solar System located roughly between the orbits of Mars and
Jupiter.
S-type (silicaceous) accounts for about 17 percent of known asteroids. Relatively bright with
an albedo of 0.10-0.22. Composition is metallic iron mixed with iron- and magnesium-silicates.
S-types dominate the inner main asteroid belt.
M-type (metallic) includes many of the rest of the known asteroids. Relatively bright with an
albedo of 0.10-0.18. Composition is apparently dominated by metallic iron. M-types inhabit the
main asteroid belt's middle region.
C-Type Asteroid Desired as the Target A small carbonaceous C-Type
asteroid with hydrated minerals is
desired, but not required, because:
Asteroids of this type and size are
known to be too weak to survive
entry through the Earth’s
atmosphere, even if it did approach
the Earth it would break up and
volatilize in the atmosphere.
- The chemical and physical
properties of these asteroids are well
understood and benign.
-- They have a very low crushing
strength and high content of
desirable volatiles.
Carbonaceous asteroids are the
most compositionally diverse
asteroids.
A carbonaceous C-type asteroid may contain volatiles (water carbon-rich compounds), metals
(iron, nickel, and cobalt), and silicate residue (similar to the average lunar surface material).
The above chart shows what may be the composition in tons (T) of a 500 ton (one million
pound) C-type asteroid.
Other Materials
~2% (~10 T)
Water
~20 %
(~10 T)
Carbon-Rich
Compounds
~20 %
(~10 T) Iron
16.6 %
(83 T)
Silicate
Residue
40 %
(200 T)
Cobalt
0.2% (1 T)
Nickel
1.2% (6 T)
Credit: Keck Institute for
Space Studies
NEO Target Detection and Characterization Need to identify Near Earth Object (NEO) targets that meet:
Trajectory
Size
Spin rate
Composition
NEO search programs:
Currently, most NEO discoveries are made by:
- Catalina Sky Survey (60%)
-- Catalina Sky Survey searches for potentially hazardous NEOs.
- Panoramic Survey Telescope and Rapid Response System-1 (30%)
-- Pan-STARRS-1 surveys celestial objects including NEOs.
- Lincoln Near-Earth Asteroid Research (3%)
-- LINEAR conducts systematic discovery and tracking of NEOs.
NEO radar observation:
Radar provides size/shape, high precision range/orbit data, spin
rate, surface density and roughness.
Sites include Goldstone Observatory, CA and Arecibo Observatory,
Puerto Rico.
NEO infrared characterization includes:
Spitzer Space Telescope - An infrared space-based observatory
launched in 2003, formerly the Space Infrared Telescope Facility
- Orbits the Sun about 109 million miles from Earth
- Provides NEO thermal signatures and albedo/sizes
Enhancements and new surveys can be online in the next two years.
Some enhancements will require additional funding.
Spitzer Telescope
Pan-STARRS-1
Catalina Sky Survey Credit: U of Arizona
Credit: U of Hawaii
Credit: NASA
2013 MFR Reference Mission Asteroid Selected
The table provides the status of the 2013 Mission Formulation Review (MFR) candidate
asteroid targets with detailed mission design analysis:
2011 MD and 2008 HU4 need further characterization;
2009 BD and 2013 EC20 are well enough understood to be valid candidate targets:
- 2013 EC20 launch is too early and likely too small to be certified;
- 2009 BD is a “valid candidate target” with an estimated size of 13.1-26.2 ft, maximum
returnable mass of 1,300,727 lbs, and a velocity of 3,937 ft/sec.
-- This candidate target is low risk for capture and detumble/despin;
-- Possible certification for selection pending Spitzer observations in January 2014.
Choosing a mission target early will reduce concerns about mission readiness and reduce
overall mission risk and cost.
Credit: NASA
period
Redirect - Asteroid Capture and Return Spacecraft Launch
The asteroid redirect and explore sequence
is based on the Asteroid Redirect Initiative
animation and the April 2, 2012 Asteroid
Retrieval Feasibility Study, Keck Institute for
Space Studies.
Initial plans will launch the Asteroid Capture
and Return (ACR) spacecraft to low Earth
orbit on an Atlas V 551-class rocket as early
as 2017.
The Atlas V 551-class rocket is shown
launching the Juno spacecraft August 5,
2011 toward Jupiter from Space Launch
Complex-41 at the Cape Canaveral Air
Force Station, FL. The 8,000 lbs Juno
spacecraft will take five years to reach
Jupiter on a mission to understand the its
origin and evolution.
The Juno 16 ft diameter payload fairing was
shorter in length than the medium fairing
required by the ACR spacecraft.
Credit: NASA and United Launch Alliance
Select Image
for Animation
ACR Spacecraft Cruises to Asteroid using Solar Electric Propulsion
Solar Array
Panels (2) Spacecraft Bus
Capture Bag
Cover
Communications
Antenna
The Asteroid Capture and Return (ACR) spacecraft cruise configuration concept is dominated
by two 35 ft diameter foldable solar array panels.
The panels generate at least 40 kilowatt electrical of power for the electric propulsion system
consisting of five Hall thrusters with 2-axis gimbals.
- The Hall thrusters are located on the aft end of the spacecraft bus. The Hall thrusters’ xenon
propellant is located in tanks inside the spacecraft bus.
The asteroid capture bag is stowed inside the cover on the front of the spacecraft bus.
A suite of instruments is used to track and characterize the asteroid.
- The instruments are located on the forward end of the spacecraft bus.
- A hole in the capture bag cover provides a field-of-view for the instruments.
A communications antenna is mounted to the spacecraft bus.
Credit: NASA
Spacecraft Capture Bag Begins Deployment Credit: NASA
Since the asteroid is only 23-32 ft wide, the spacecraft would likely need to implement a search
to encounter the target.
The asteroid should be visible from a distance of 62,000 to 124,000 miles.
During the months prior to rendezvous, images and range measurements would determine the
asteroid’s position.
- Preliminary information for further approach and close-up characterization would also be
collected.
After the stowed capture bag’s protective cover is jettisoned, the bag would start to deploy.
The capture bag conceptual mechanisms includes inflatable deployable arms, a high-strength
bag assembly, and cinching cables.
Spacecraft with Capture Bag Fully Deployed Approaches Asteroid
Credit: NASA
When the capture bag is inflated and rigidized, four or more arms connected by two or more
inflated circumferential hoops provide the compressive strength to hold the bag open.
The bag would be roughly 50 ft in diameter by 33 ft long.
- The capture mechanism concept could accommodate a wide range of uncertainty in the
shape and strength of the asteroid.
The capture process must consider a tumbling, non-cooperative object.
Spacecraft Rendezvous with Asteroid
Credit: NASA
In the far-approach phase, the spacecraft would approach and loiter in the vicinity of the
asteroid.
The range to the target may be a mile at this point.
In the middle-approach phase, the spacecraft would be brought to within about 600 ft of the
target and parked there for an extended period of time.
A radar altimeter should be able to be used during this phase to maintain station-keeping.
Full characterization of the asteroid would be done at distances from 0.6 mile to 300 ft using
a suite of instruments including:
- A spectrometer would be considered for measuring the surface composition.
- A 1-2 Hertz frame rate camera could be used for resolving the spin state.
Spacecraft Matches Asteroid Rotation
Credit: NASA
Sometime after the spin state has been identified, the spacecraft would approach the asteroid
by following a series of closure steps consisting of several descent-station keeping cycles. The
view above is looking at the asteroid from within the capture bag.
The guidance subsystem would use radar-altimeter aided relative position estimates to plan
and execute these trajectories.
The final station-keeping location may be tens of yards from the asteroid center.
The spacecraft would then match the surface velocity and primary spin state of the asteroid
while maintaining position at the final station-keeping location.
Capture Bag Starts to Trap Asteroid
Credit: NASA
During capture, the asteroid would be positioned inside the capture bag and there would only
be a small residual relative velocity between the asteroid surface and the capture bag.
Cameras on the solar array supports would be used to verify proper capture bag deployment
and subsequently to aid in the asteroid capture.
A ring would be between the capture bag and the forward end of the spacecraft to impart
forces on the asteroid through the bag.
Capture Bag Starts to Secure Asteroid to Spacecraft
Credit: NASA
To capture the asteroid, multiple "draw strings" would cinch-close the opening of the bag and
also cinch-tight against the asteroid.
Due to the residual velocity between the asteroid and the spacecraft, some “impact” is
expected when the asteroid is captured.
- Since the asteroid would be much more massive than the spacecraft, it is perhaps better to
think of this as the asteroid capturing the spacecraft.
The tightly-cinched bag containing the asteroid would be drawn up against the ring that
constrains its position and attitude so that its center-of-mass is controlled, and forces and
torques could be applied by the spacecraft during transportation to the Moon.
Spacecraft Propels Secured Asteroid to Cis-Lunar Space
Credit: NASA
Reaction Control
Thrusters Pod (4)
Once the spacecraft and asteroid are tightly secured together, the spacecraft would de-tumble
the combination using four reaction control system thruster pods mounted to the spacecraft.
The four thruster pods would control the attitude when the electric propulsion system (EPS) is
not operating.
The EPS would then transport the spacecraft and asteroid combination to cis-lunar space
(between the Earth and Moon).
The image above shows the combination cruising toward cis-lunar space using the EPS.
- Thrusting with the EPS would be the normal operating mode during the mission.
- Attitude control during EPS thrusting would be provided by gimbaling the Hall thrusters.
Explore - Asteroid Mission Crew Launched
Credit: NASA
After the ACR spacecraft robotically captures the asteroid, and the combination parks in cis-
lunar space, NASA plans to send at least two astronauts to the asteroid to investigate and
collect samples as early as 2021. This would be the first crewed flight of the Orion Multi-
Purpose Crew Vehicle. Orion is shown being launched by the Space Launch System from
Kennedy Space Center, FL.
Orion Crew Begins Journey to Captured Asteroid Credit: NASA
Service
Module
Crew
Module
Following the separation of Orion from the Interim Cryogenic Propulsion Stage, the vehicle
starts to cruise to the ACR spacecraft/asteroid combination parked in cis-lunar space.
Orion will serve as the primary crew vehicle for missions beyond low Earth orbit (LEO).
- It is capable of conducting regular in-space operations (rendezvous, docking, extravehicular
activity) in conjunction with missions beyond LEO and Orion consists of:
-- Crew Module - the 16.5 ft diameter by 10.83 ft long transportation capsule provides a safe
habitat for the crew, storage for consumables and research instruments, and serves as the
docking port for crew transfer.
--- The crew module is the only part of Orion that returns to Earth.
-- Service Module - supports the crew module from launch through separation prior to re-entry
providing propulsion capability for orbital transfer, attitude control, and high altitude ascent
aborts as well as consumables needed to maintain a habitable environment.
Following the separation of Orion from the Interim Cryogenic Propulsion Stage, the vehicle
starts its cruise, moves around the Moon, and then begins its rendezvous maneuvers with the
ACR spacecraft/asteroid combination parked in high lunar orbit. Orion completes the
rendezvous with the combination where the path changes from red to green.
Orion Crew Starts Rendezvous with ACR Spacecraft/Asteroid
Orion
ACR Spacecraft/
Asteroid
Moon
Orion’s Cruise
Path from Earth
High Lunar
Orbit
Credit NASA
Orion’s Robotic Arm Grapples ACR Spacecraft
Credit: NASA
When Orion has approached within a few yards of the ACR spacecraft/asteroid combination,
the astronauts begin the docking operations.
Orion maneuvers until its forward end faces the aft end of the ACR spacecraft and the
centers of the two vehicles coincide.
Orion’s robotic arm is released from stowage and it’s end effector secures the ACR
spacecraft’s grapple fixture completing docking.
- The above shows a view from Orion looking at the aft end of the ACR spacecraft prior to the
robotic arm end effector attaching to the ACR spacecraft’s grapple fixture.
-- The green text indicates navigation (left) and robotic arm status to the crew.
-- Three of the ACR spacecraft’s Hall thruster/gimbals are shown centered on the aft end.
-- The capture bag/asteroid can be seen to the right and upper left of the spacecraft’s aft end.
-- One of the four reaction control thrusters pods can be seen below the grapple fixture.
Orion Crew Prepare to Explore Asteroid
After docking Orion to the ACR spacecraft/asteroid combination, the astronauts prepare to
spacewalk from the Crew Module to the aft end of the capture bag to investigate the asteroid.
The NASA Extreme Environment Mission Operations (NEEMO) missions in 2011 and 2012
simulated several challenges the crew will face when visiting an asteroid including how to move
around its surface and how to collect samples.
NASA has also simulated an asteroid mission as part of its 2012 Research and Technology
Studies ground test at Johnson Space Center, TX.
- During the simulation, a team evaluated how astronauts might do a spacewalk on an asteroid
and accomplish other goals.
Credit: NASA
Two Astronauts Spacewalk from Orion to ACR Spacecraft
After exiting Orion’s side hatch and installing a telescoping mobility aid, an astronaut is shown
moving to the ACR spacecraft using the aid as a handrail. Another astronaut, inside Orion, is
observing and will also use the aid to move to the spacecraft. A sample container is tethered to
Orion.
The first extravehicular activity (EVA) is initially planned for the day after Orion docks to the
ACR spacecraft/asteroid combination and a second EVA is planned for the third day after
docking.
Credit: NASA
Sample
Container
Asteroid Target Exploration and Characterization
Credit: NASA
After reaching the aft end of the capture bag, installing a foot restraint, and opening the bag,
the astronauts start to explore the asteroid.
The astronaut, restrained by the foot restraint (left), is photographing the asteroid.
The other astronaut is handling a sample container.
The immediate science goals of the mission are to understand the physical and chemical
history of the asteroid.
- Certain classical analytical procedures, such as assays for the content of a wide variety of
organic constituents, could easily be done on small samples (about one pound would qualify as
a “huge” sample).
Astronauts Stow Asteroid Samples in Orion
Credit: NASA
Upon completion of the asteroid exploration, the astronauts return to Orion with the sample
containers and other equipment used on the EVA. After passing the containers and equipment
through the side hatch, they would be stowed for the trip back to Earth.
Orion Releases ACR Spacecraft with Asteroid
Credit: NASA
Orion’s robotic arm releases the ACR spacecraft/asteroid combination after 5 days of
exploration.
- The astronauts performed two spacewalks on two separate days investigating the asteroid.
- Orion will now begin the journey back by first looping around the Moon and then returning to
Earth in 6 days after leaving the combination.
The combination will continue to orbit the Moon to enable further exploration of the asteroid.
- The electric propulsion system xenon propellant resupply or an additional propulsion module
may be necessary to maintain station-keeping of the combination in lunar orbit.
Orion Crew Separates from Service Module for Re-Entry
Credit: NASA
After the Orion service module (SM) separates from the crew module (CM), the CM enters the
atmosphere at a speed over 20,000 miles per hour. The SM will enter the atmosphere and burn
up.
Orion Crew Returns
Credit: NASA
The Orion crew module (CM) approaches splashdown in the Pacific Ocean prior to the end of
the 22 day asteroid retrieval and utilization mission. After returning to Earth, the CM will be
tethered and pulled into the well deck of a Navy ship for its trip back to dry land in Long Beach,
CA.
MFR Asteroid Redirect Robotic Vehicle (ARRV) Concepts
The Mission Formulation Review (MFR) developed two ARRV configuration concepts:
1) Roll Out Solar Array (ROSA) Configuration - features an ARRV with a flexible blanket solar
array (SA) developed by Deployable Space Systems.
2) MegaFlex Configuration - has an ARRV with an accordion fanfold flexible blanket SA built
by ATK Space Systems.
1) ROSA
(Stowed)
2) MegaFlex
(Stowed)
1) ROSA
(Deployed)
2) MegaFlex
(Deployed)
Credit: NASA
ARRV configuration concepts based
on Space Technology Mission
Directorate (STMD) SA development.
MFR ARRV Baseline Concept
Credit: NASA
The MFR ARRV baseline concept is
comprised of:
Capture Mechanism - captures a
wide range of spinning/tumbling
asteroids.
Mission Module - flight heritage deep
space avionics packaged in modules.
Solar Electric Propulsion (SEP)
Module includes:
- Ion Propulsion - 4 Hall thrusters with
gimbals fueled by 22,046 lbs of xenon
in 8 seamless tanks, 50 kilowatt solar
arrays with solar array drives, and
power management and distribution
system;
- Mechanical & Structure -
conventional construction;
- Thermal Control - conventional cold
plates with heat-pipe radiators;
- Reaction Control - conventional
hydrazine monopropellant system.
Launch Adapter - transition structure
mounting the ARRV to the launch
vehicle (Atlas V, SLS or Falcon H).
MFR ARRV Capture Mechanism Concept
Credit: NASA
The 49 ft diameter fabric capture bag
consists of a cylindrical barrel section
and conical section attached to the
spacecraft, and includes:
An inflatable exoskeleton that deploys
the bag after arrival at the asteroid;
Inflatable "stack of torroids" at the
base of the cone forms a passive
cushion between the asteroid and the
spacecraft;
Circumferential cinch winches close
the diaphragm at the top of the
cylindrical section confining the asteroid
after the capture bag deflates;
Air bags quickly immobilize the
capture bag and asteroid at a very low
contact pressure;
Axial cinch winches control motion, re-
track bag, and position asteroid center-
of-mass.
The capture mechanism limits the
forces on the ARRV solar arrays from
the spacecraft/asteroid combination
rotational motions.
Air Bags
ARRV
Spacecraft
MFR Capture Sequence and Capture Testbed
The asteroid capture sequence is initiated when the spacecraft
approaches and matches the asteroid spin rate and continues:
The top diaphragm is closed after the asteroid is centered in the
capture bag;
At the moment the asteroid spin rate is matched, the air bags
inside the capture bag inflate limiting the loads on the asteroid
surface and achieving a controlled capture;
The asteroid is cinched tightly to the spacecraft while the capture
bag is venting.
The initial one-eighth scale capture testbed (right) has an inflatable
exoskeleton with winches suspended from a gantry over the
asteroid.
- A robot arm, attached to the asteroid, can spin and tumble it.
Credit: NASA
Asteroid Redirect Crewed Mission MFR Summary
The crewed mission is technically feasible.
The design accommodates predicted Orion Exploration Mission-2 (EM-2) performance with
the inclusion of mission kits for: rendezvous and docking, extravehicular activity (EVA), and
asteroid sample curation.
There are no significant changes to the Orion and Space Launch System requirements.
The crewed mission cost and schedule are feasible.
Mission risks are mitigated with the appropriate flight testing including:
- Employing EM-1 and 2 flight test strategy;
- Leveraging the International Space Station as an exploration test bed;
- Using the prior space shuttle flight test STORRM (Sensor Test for Orion Relative Navigation
Risk Mitigation) rendezvous and docking sensors.
-- STORRM successfully demonstrated new technology to make rendezvous and docking
easier and safer.
Credit: NASA
Orion/Asteroid Redirect Robotic Vehicle
(ARRV) concept rendezvous and
docking system, and EVA tools revised.
Orion
ARRV with
Asteroid
MFR Crewed Mission Trajectory & Schedule
Legend:
TLI - Trans-Lunar Injection
DRO - Distant Retrograde Orbit
ARV - Asteroid Redirect Robotic Vehicle
MECO - Main Engine Cut Off
EI - Entry Interface
EVA - Extravehicular Activity
Credit: NASA
Mission duration and timing of specific events
will vary slightly based on the launch date.
I
MFR Crewed Mission ARRV Rendezvous and Docking
Legend:
ARRV - Asteroid Redirect Robotic Vehicle
IDSS - International Docking System Standard LED - Light Emitting Diode
LIDAR - Light Detection and Ranging
Credit: NASA
• The minimum ARRV hardware to accommodate Orion rendezvous and docking was identified
using the International Docking System Standard.
MFR Rendezvous and Docking Mission Kits
• is
• is
Credit: NASA
The Relative Navigation Sensor Kit, mounted to the Orion hatch, is the primary navigation
instrument used by the spacecraft during rendezvous, proximity operations, and docking.
MFR Crewed Mission ARRV EVA Accommodations
Legend:
ARRV & ARV - Asteroid Redirect Robotic Vehicle
EVA - Extravehicular Activity
Credit: NASA
EVA Translation Booms
• Translation booms for asteroid EVA
• Tool box stores 187 lbs tools
MFR Suit & EVA Mission Kits
Legend:
AES - Advanced Exploration Systems
EVA - Extravehicular Activity
ISS - International Space Station
NBL - Neutral Buoyancy Laboratory
PLSS - Portable Life Support System
Assumes Government Furnished Equipment for EVA support kits
Four kits were identified to enable Orion capsule-based EVA capability
Credit: NASA
MACES Capsule-Based EVA Development Plan
Legend:
AES - Advanced Exploration Systems
ISS - International Space Station
NBL - Neutral Buoyancy Laboratory
Credit: NASA
MACES - Modified Advanced Crew Escape Suit is an upgraded version of the Advanced Crew Escape Suit
that astronauts donned for the launch and entry phases of shuttle operations.
Leverages existing AES, Orion and ISS investments
NASA Future Activities 2014 Major Activities (as of April 10, 2013)
The Science Mission Directorate’s Planetary Science Program plans to:
- Implement the systematic focus on candidate targets using ground assets;
- Begin the study of a space-based observation platform.
The Space Technology Mission Directorate plans to:
- Accelerate the development of a demonstration of a high power solar electric propulsion
system including:
-- Begin the design and test of a large-scale solar electric array leveraging investment in the
ground demonstration of large arrays that was initiated in 2012;
-- Design and build engineering units of the high power electronics and ion thruster engines;
-- Design a large quantity xenon propellant tank.
- Engage academic and industry for ideas and concepts regarding asteroid capture,
characterization, sampling, and resource utilization.
Human Exploration and Operations Mission Directorate’s Advanced Exploration Systems
plans to:
- Begin the development of an asteroid capture mechanism;
- Investigate spacecraft control algorithms for capturing and redirecting an asteroid;
- Demonstrate concepts for astronaut extravehicular activity on the surface of an asteroid.
Credit: NASA
Reference Information
Text and Images:mages
http://www.nasa.gov/
http://www.youtube.com/
http://en.wikipedia.org/
http://www.kiss.caltech.edu/
http://nssdc.gsfc.nasa.gov/
http://www.lpl.arizona.edu/
http://pan-starrs.ifa.hawaii.edu/
http://astronomy2009.nasa.gov/
Project Orion Overview and Prime Contractor Announcement, Skip Hatfield, NASA Orion
Project Manager, August 31, 2006 - presentation includes crew module configuration
Asteroid Redirect Initiative Video: http://www.nasa.gov/mission_pages/asteroids/news/asteroid_initiative.html
End